EP1840337A1 - Joint de rainure et languette entre deux composants de turbine - Google Patents

Joint de rainure et languette entre deux composants de turbine Download PDF

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Publication number
EP1840337A1
EP1840337A1 EP06006938A EP06006938A EP1840337A1 EP 1840337 A1 EP1840337 A1 EP 1840337A1 EP 06006938 A EP06006938 A EP 06006938A EP 06006938 A EP06006938 A EP 06006938A EP 1840337 A1 EP1840337 A1 EP 1840337A1
Authority
EP
European Patent Office
Prior art keywords
turbine
groove
components
tongue
filling material
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP06006938A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Rostislav Teteruk
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP06006938A priority Critical patent/EP1840337A1/fr
Publication of EP1840337A1 publication Critical patent/EP1840337A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/506—Hardness
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the invention relates to a turbine with a number of turbine components, in which a first turbine component is connected via a tongue and groove connection with a second turbine component.
  • Turbines in particular gas turbines, are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel which is under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined to form groups of blades or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
  • To guide the working fluid in the turbine unit also usually connected between adjacent blade rows are connected to the turbine housing Leitschaufelhalln.
  • the turbine components forming this flow channel for the working medium are usually connected to one another via tongue-and-groove connections.
  • an integrally formed on one of the turbine components mounting lip engages in an associated groove in the second turbine component.
  • Such connection techniques are usually chosen to keep Abström maste and leaks as low as possible and thus to lead the working fluid in the flow channel particularly effective through the blade rows.
  • such groove-and-tongue connections between individual turbine components are usually designed with particularly high accuracy of fit and with particularly low tolerances, so that due to the high accuracy of fit unwanted leakage losses can be kept particularly low.
  • the invention is therefore based on the object of specifying a turbine of the type mentioned above, in which the leakage losses can be kept particularly low with particularly low assembly and manufacturing costs during operation of the turbine.
  • This object is achieved according to the invention in that a groove formed between groove and tongue is filled with a filling material in the tongue-and-groove joint connecting the first and the second turbine components.
  • the invention is based on the consideration that, for particularly low leakage losses, a particularly high tightness between the mutually connected turbine components should be ensured.
  • the possibilities for this are limited in the utilization of manufacturing accuracies and the like, in particular because of systemic effects due to thermal stress additional gap formations could occur.
  • the turbine components should therefore have a suitably selected sealing element or sealing material in the region of their connection. This can be achieved by a suitable filling material is provided in the region of a gap formed between tongue and groove, which can deform plastically, for example, during assembly of the two components and in the production of tongue and groove connection and thus manufacturing inaccuracies of the actual component parts suitable compensates.
  • a suitable filling material is provided in the region of a gap formed between tongue and groove, which can deform plastically, for example, during assembly of the two components and in the production of tongue and groove connection and thus manufacturing inaccuracies of the actual component parts suitable compensates.
  • a softer material than the material of the turbine components is advantageously selected as the filling material.
  • a softer material than the material of the turbine components is advantageously selected as the filling material.
  • the turbine is designed as a gas turbine.
  • the tongue-and-groove connection provided with the filling material is preferably used in turbine components which are used in the region of the flow space for the working medium.
  • the tongue-and-groove connection with the filling material connects a guide vane to a guide vane carrier or a vane to an end piece of a combustion chamber wall or a guide ring segment with its holder.
  • the advantages achieved by the invention are, in particular, that a particularly high density of the interconnected turbine components can be achieved by the introduction of the filling material in the gap formed between the tongue and groove of the tongue and groove joint.
  • the turbine components can be manufactured with comparatively generously dimensioned manufacturing tolerances, since fit inaccuracies and the like can be compensated appropriately in the installed state via the filling material anyway.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator or a working machine (not shown).
  • the turbine 6 and the compressor 2 are arranged on a common, also called turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its central axis 9.
  • the combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel. It is also provided on its inner wall with heat shield elements not shown.
  • the turbine 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine 6 comprises a number of fixed vanes 14, which are also fixed in a ring shape to form an airfoil on an inner casing 16 of the turbine 6.
  • the blades 12 are used to drive the turbine shaft 8 by momentum transfer from a turbine 6 flowing through the working medium M.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of vanes 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18, which is arranged to fix the respective vane 14 on the inner housing 16 of the turbine 6 as a wall element.
  • the platform 18 is a thermally comparatively heavily loaded component which defines the outer boundary of a hot gas channel for the turbine 6 flowing through the working medium M forms.
  • Each blade 12 is attached to the turbine shaft 8 in an analogous manner via a platform 20, also referred to as a blade root.
  • each guide ring 21 on the inner housing 16 of the turbine 6 is arranged between the spaced-apart platforms 18 of the guide vanes 14 of two adjacent rows of guide vanes.
  • the inner surface of each guide ring 21 is also exposed to the hot working medium M flowing through the turbine 6 and spaced radially from the outer end 22 of the blades 12 of a blade row opposite it through a gap 24.
  • the arranged between adjacent rows of guide vanes 21 serve as a by their thermal expansion, the gap 24 between the respective guide ring 21 and associated blade row regulating components and on the other as cover that the inner housing 16 or other housing-mounting components from thermal overload by the Turbine 6 through flowing hot working medium M protect.
  • a tongue-and-groove connection Several of the turbine components forming the turbine 6, in particular the turbine components arranged in the region of the hot gas duct, are connected to the respectively adjacent turbine components via a tongue-and-groove connection.
  • some of these tongue-and-groove joints are made with a specifically selected filling material prepared, as shown by way of example in Fig. 2 is.
  • a first turbine component 30 is shown, which has an integrally formed, in a longitudinal direction extending mounting lip to form a spring 32.
  • the spring 32 engages in an associated groove 34 of a second turbine component 36 for producing the tongue-and-groove connection.
  • the gap 38 formed between the groove 34 and the spring 32 is filled with a filling material 40.
  • a material which is softer than the material of the actual turbine components 30, 36 is selected as filler material 40.
  • the spring 32 When mounting the turbine components 30,36, the spring 32 is inserted or introduced into the groove 34.
  • the filling material 40 is suitably shaped beforehand, for example in the form of a thickly applied coating either on the spring 32 or in the groove 34 or else in the manner of a suitably chosen starting body, such as a long-drawn wire or the like , introduced into the region between the groove 34 and the spring 32.
  • the filling material 40 is suitably deformed and thus fills the gap 38 almost completely. Production inaccuracies and the like are thereby compensated, so that a tight connection between the turbine components 30,36 arises.
  • a soldering material or the like is considered as filling material 40, which is attached to one of the two turbine components 30, 36, for example, in a materially bonded manner.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06006938A 2006-03-31 2006-03-31 Joint de rainure et languette entre deux composants de turbine Withdrawn EP1840337A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06006938A EP1840337A1 (fr) 2006-03-31 2006-03-31 Joint de rainure et languette entre deux composants de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06006938A EP1840337A1 (fr) 2006-03-31 2006-03-31 Joint de rainure et languette entre deux composants de turbine

Publications (1)

Publication Number Publication Date
EP1840337A1 true EP1840337A1 (fr) 2007-10-03

Family

ID=36888897

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06006938A Withdrawn EP1840337A1 (fr) 2006-03-31 2006-03-31 Joint de rainure et languette entre deux composants de turbine

Country Status (1)

Country Link
EP (1) EP1840337A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101672300A (zh) * 2008-09-12 2010-03-17 通用电气公司 燃气涡轮机叶片连接
EP2206885A1 (fr) * 2009-01-08 2010-07-14 Siemens Aktiengesellschaft Turbine à gaz
EP2211023A1 (fr) * 2009-01-21 2010-07-28 Siemens Aktiengesellschaft Distributeur pour turbomachine avec structure support d'aubes directrices segmentée
EP3023594A1 (fr) * 2014-10-22 2016-05-25 United Technologies Corporation Ensemble de stator avec interface de tampon pour une turbine à gaz

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2936155A (en) * 1951-12-10 1960-05-10 Power Jets Res & Dev Ltd Resiliently mounted turbine blades
CH423431A (de) * 1965-10-13 1966-10-31 Licentia Gmbh Verfahren zur Herstellung eines Strömungsmaschinenschaufelfusses und/oder dessen am Schaufelträger befindlichen Halterung
DE2250563A1 (de) * 1971-11-03 1973-05-10 British Leyland Truck & Bus Turbinen-rotor
US3784320A (en) * 1971-02-20 1974-01-08 Motoren Turbinen Union Method and means for retaining ceramic turbine blades
US4417854A (en) * 1980-03-21 1983-11-29 Rockwell International Corporation Compliant interface for ceramic turbine blades
US4552509A (en) * 1980-01-31 1985-11-12 Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for joining two relatively rotatable turbomachine components
EP1035377A2 (fr) * 1999-03-08 2000-09-13 Mitsubishi Heavy Industries, Ltd. Joint d'étanchéitée pour la partie aval d'une chambre de combustion d'une turbine à gaz
US20020189722A1 (en) * 1999-06-29 2002-12-19 Hasz Wayne Charles Turbine engine component having wear coating and method for coating a turbine engine component
EP1491720A1 (fr) * 2003-06-25 2004-12-29 General Electric Company Procédé d'amélioration de la résistance à l'usure d'une region de support entre un carter de turbine et une aube statorique
EP1561905A1 (fr) * 2004-02-09 2005-08-10 Siemens Aktiengesellschaft Couche plastiquement déformable dans la région de fixation d'une aube de turbine et procédé de fixation d'une telle aube
EP1584792A1 (fr) * 2004-04-08 2005-10-12 Siemens Aktiengesellschaft Attachement d'aube pour un compresseur ou une turbine

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2936155A (en) * 1951-12-10 1960-05-10 Power Jets Res & Dev Ltd Resiliently mounted turbine blades
CH423431A (de) * 1965-10-13 1966-10-31 Licentia Gmbh Verfahren zur Herstellung eines Strömungsmaschinenschaufelfusses und/oder dessen am Schaufelträger befindlichen Halterung
US3784320A (en) * 1971-02-20 1974-01-08 Motoren Turbinen Union Method and means for retaining ceramic turbine blades
DE2250563A1 (de) * 1971-11-03 1973-05-10 British Leyland Truck & Bus Turbinen-rotor
US4552509A (en) * 1980-01-31 1985-11-12 Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for joining two relatively rotatable turbomachine components
US4417854A (en) * 1980-03-21 1983-11-29 Rockwell International Corporation Compliant interface for ceramic turbine blades
EP1035377A2 (fr) * 1999-03-08 2000-09-13 Mitsubishi Heavy Industries, Ltd. Joint d'étanchéitée pour la partie aval d'une chambre de combustion d'une turbine à gaz
US20020189722A1 (en) * 1999-06-29 2002-12-19 Hasz Wayne Charles Turbine engine component having wear coating and method for coating a turbine engine component
EP1491720A1 (fr) * 2003-06-25 2004-12-29 General Electric Company Procédé d'amélioration de la résistance à l'usure d'une region de support entre un carter de turbine et une aube statorique
EP1561905A1 (fr) * 2004-02-09 2005-08-10 Siemens Aktiengesellschaft Couche plastiquement déformable dans la région de fixation d'une aube de turbine et procédé de fixation d'une telle aube
EP1584792A1 (fr) * 2004-04-08 2005-10-12 Siemens Aktiengesellschaft Attachement d'aube pour un compresseur ou une turbine

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101672300A (zh) * 2008-09-12 2010-03-17 通用电气公司 燃气涡轮机叶片连接
EP2163734A2 (fr) * 2008-09-12 2010-03-17 General Electric Company Dispositif de fixation d'aubes statoriques de turbine à gaz
EP2163734A3 (fr) * 2008-09-12 2012-11-07 General Electric Company Dispositif de fixation d'aubes statoriques de turbine à gaz
EP2206885A1 (fr) * 2009-01-08 2010-07-14 Siemens Aktiengesellschaft Turbine à gaz
EP2211023A1 (fr) * 2009-01-21 2010-07-28 Siemens Aktiengesellschaft Distributeur pour turbomachine avec structure support d'aubes directrices segmentée
WO2010084028A1 (fr) * 2009-01-21 2010-07-29 Siemens Aktiengesellschaft Système d'aubes directrices pour une turbomachine comportant un support d'aubes directrices segmenté
US9238976B2 (en) 2009-01-21 2016-01-19 Siemens Aktiengesellschaft Guide vane system for a turbomachine having segmented guide vane carriers
EP3023594A1 (fr) * 2014-10-22 2016-05-25 United Technologies Corporation Ensemble de stator avec interface de tampon pour une turbine à gaz
US10036263B2 (en) 2014-10-22 2018-07-31 United Technologies Corporation Stator assembly with pad interface for a gas turbine engine

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